A temperature modeling method for the servo actuator of aero-engine

The servo actuator is a key component of the aero-engine, and often operated in extreme high-temperature conditions. Developing a thermal model of servo actuator, and analyzing its heat transfer mechanisms, temperature variation laws, and key influencing factors is of great significance in ensuring its optimal performance under extreme working conditions. To address this issue, a theoretical method of temperature modeling is proposed for the servo actuator. Based on the actual working conditions of the servo actuator in the aero-engine, a lumped parameter method is adopted to explore the heat exchange mechanisms. And a thermodynamic mathematical model is further established for each component of the servo actuator in the two different working states. The analysis results show that the temperature at each node during reciprocating movement is lower than the condition when the piston rod is moved to the middle position and fixed. In addition, the radiation temperature has the most significant impact on the cylinder barrel, and oil temperature is linearly related to the thermal equilibrium temperature of each component. When the cooling orifice diameter surpasses 0.4 mm and continues to increase, the reduction in temperature of each actuator component becomes less pronounced. Simulation analysis and high-temperature tests verify the correctness of the proposed theoretical model for the servo actuator of aero-engine. The proposed temperature modeling and analysis method can be used to guide the design and analysis of servo actuators under high-temperature conditions.